Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

RAE 5214 AIRFOIL (rae5214-il)

RAE 5214 AIRFOIL - RAE 5214 transonic airfoil


Airfoil rae5214-il
Details Dat file Parser  
(rae5214-il) RAE 5214 AIRFOIL
RAE 5214 transonic airfoil
Max thickness 9.7% at 35.5% chord.
Max camber 1.4% at 69.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 RAE 5214 AIRFOIL
       42.       42.
 
 0.00000   0.00000
 0.00050   0.00522
 0.00100   0.00732
 0.00160   0.00925
 0.00241   0.01128
 0.00350   0.01343
 0.00500   0.01580
 0.00650   0.01778
 0.00800   0.01940
 0.00961   0.02090
 0.01500   0.02480
 0.02153   0.02841
 0.03000   0.03216
 0.03806   0.03496
 0.05904   0.04029
 0.08427   0.04434
 0.11349   0.04776
 0.14645   0.05045
 0.18280   0.05276
 0.22221   0.05480
 0.26430   0.05640
 0.30866   0.05744
 0.35486   0.05778
 0.40245   0.05742
 0.45099   0.05642
 0.50000   0.05478
 0.54901   0.05234
 0.59755   0.04917
 0.64514   0.04524
 0.69134   0.04071
 0.73570   0.03586
 0.77779   0.03082
 0.81720   0.02581
 0.85355   0.02094
 0.88651   0.01641
 0.91573   0.01236
 0.94096   0.00870
 0.96194   0.00562
 0.97847   0.00302
 0.99039   0.00133
 0.99759   0.00034
 1.00000   0.00000
 
 0.00000   0.00000
 0.00050  -0.00410
 0.00100  -0.00545
 0.00160  -0.00665
 0.00241  -0.00785
 0.00350  -0.00900
 0.00500  -0.01030
 0.00650  -0.01139
 0.00800  -0.01228
 0.00961  -0.01316
 0.01500  -0.01533
 0.02153  -0.01727
 0.03000  -0.01947
 0.03806  -0.02118
 0.05904  -0.02459
 0.08427  -0.02786
 0.11349  -0.03074
 0.14645  -0.03332
 0.18280  -0.03556
 0.22221  -0.03731
 0.26430  -0.03856
 0.30866  -0.03915
 0.35486  -0.03889
 0.40245  -0.03773
 0.45099  -0.03560
 0.50000  -0.03232
 0.54901  -0.02788
 0.59755  -0.02267
 0.64514  -0.01716
 0.69134  -0.01199
 0.73570  -0.00768
 0.77779  -0.00424
 0.81720  -0.00175
 0.85355  -0.00010
 0.88651   0.00085
 0.91573   0.00130
 0.94096   0.00126
 0.96194   0.00098
 0.97847   0.00062
 0.99039   0.00029
 0.99759   0.00006
 1.00000   0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

RAE 5215 AIRFOILPreviewDetails
RAE(NPL) 5213 AIRFOILPreviewDetails
YS-915PreviewDetails
NACA 63-210 AIRFOILPreviewDetails
NPL AIRFOIL FROM ARC CP 1372PreviewDetails
S2050 8.93%PreviewDetails
EPPLER E851 AIRFOILPreviewDetails
BOEING AIRFOIL J (no closed TE)PreviewDetails
NLR-7223-43 AIRFOILPreviewDetails
GOE 599 AIRFOILPreviewDetails

Polars for RAE 5214 AIRFOIL (rae5214-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae5214-il50,000929.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5214-il50,000527.5 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5214-il100,000940.3 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5214-il100,000535.7 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5214-il200,000946.4 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5214-il200,000549.1 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5214-il500,000966.6 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5214-il500,000568.4 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5214-il1,000,000983.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5214-il1,000,000580.7 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit